CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 200,000 Max Cl/Cd: 72.35 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkx-il-200000-n5.txt Download as CSV file: xf-clarkx-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK X AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4584 0.10017 0.09628 -0.0413 1.0000 0.0328
-11.000 -0.6655 0.05211 0.04824 -0.0748 1.0000 0.0335
-10.750 -0.7068 0.04773 0.04374 -0.0729 1.0000 0.0334
-10.500 -0.7437 0.04323 0.03893 -0.0696 1.0000 0.0335
-10.250 -0.7511 0.04017 0.03564 -0.0680 0.9987 0.0340
-10.000 -0.7216 0.03971 0.03521 -0.0696 0.9956 0.0348
-9.750 -0.6943 0.03871 0.03412 -0.0715 0.9918 0.0358
-9.500 -0.6716 0.03642 0.03157 -0.0736 0.9870 0.0370
-9.250 -0.6500 0.03344 0.02817 -0.0757 0.9825 0.0385
-9.000 -0.6287 0.03064 0.02484 -0.0770 0.9768 0.0400
-8.750 -0.6018 0.02833 0.02206 -0.0787 0.9734 0.0412
-8.500 -0.5768 0.02688 0.02049 -0.0793 0.9682 0.0421
-8.250 -0.5469 0.02595 0.01947 -0.0806 0.9642 0.0432
-8.000 -0.5149 0.02504 0.01842 -0.0822 0.9614 0.0445
-7.750 -0.4879 0.02398 0.01715 -0.0826 0.9561 0.0458
-7.500 -0.4598 0.02280 0.01574 -0.0832 0.9511 0.0470
-7.250 -0.4286 0.02168 0.01438 -0.0844 0.9476 0.0482
-7.000 -0.4007 0.02079 0.01328 -0.0847 0.9422 0.0493
-6.750 -0.3731 0.01985 0.01220 -0.0849 0.9364 0.0507
-6.500 -0.3421 0.01908 0.01140 -0.0859 0.9324 0.0522
-6.250 -0.3147 0.01848 0.01074 -0.0860 0.9262 0.0537
-6.000 -0.2865 0.01786 0.01004 -0.0862 0.9201 0.0552
-5.750 -0.2556 0.01723 0.00931 -0.0868 0.9157 0.0570
-5.500 -0.2298 0.01672 0.00870 -0.0864 0.9080 0.0588
-5.250 -0.2006 0.01624 0.00811 -0.0867 0.9022 0.0605
-5.000 -0.1738 0.01562 0.00751 -0.0866 0.8955 0.0633
-4.750 -0.1464 0.01523 0.00710 -0.0865 0.8883 0.0663
-4.500 -0.1179 0.01485 0.00665 -0.0866 0.8823 0.0696
-4.250 -0.0913 0.01452 0.00623 -0.0862 0.8742 0.0724
-4.000 -0.0633 0.01405 0.00577 -0.0863 0.8682 0.0764
-3.750 -0.0372 0.01377 0.00547 -0.0859 0.8596 0.0812
-3.500 -0.0087 0.01349 0.00512 -0.0859 0.8534 0.0870
-3.250 0.0172 0.01320 0.00487 -0.0855 0.8445 0.0941
-3.000 0.0454 0.01294 0.00458 -0.0855 0.8379 0.1026
-2.750 0.0718 0.01272 0.00438 -0.0852 0.8291 0.1147
-2.500 0.0994 0.01246 0.00415 -0.0850 0.8220 0.1315
-2.250 0.1258 0.01222 0.00397 -0.0848 0.8131 0.1530
-2.000 0.1527 0.01193 0.00379 -0.0846 0.8056 0.1865
-1.750 0.1788 0.01165 0.00372 -0.0843 0.7967 0.2429
-1.500 0.2057 0.01146 0.00362 -0.0841 0.7886 0.2893
-1.250 0.2323 0.01127 0.00353 -0.0838 0.7798 0.3298
-1.000 0.2585 0.01107 0.00346 -0.0834 0.7708 0.3739
-0.750 0.2843 0.01080 0.00338 -0.0830 0.7620 0.4380
-0.500 0.3083 0.01046 0.00337 -0.0821 0.7518 0.5328
-0.250 0.3298 0.00999 0.00339 -0.0805 0.7423 0.6775
0.000 0.3538 0.00965 0.00351 -0.0787 0.7324 0.8398
0.250 0.3991 0.00962 0.00354 -0.0817 0.7221 0.9396
0.500 0.4408 0.00966 0.00349 -0.0844 0.7123 0.9743
0.750 0.4859 0.00969 0.00344 -0.0880 0.7014 0.9966
1.000 0.5148 0.00976 0.00343 -0.0883 0.6905 1.0000
1.250 0.5393 0.00984 0.00342 -0.0876 0.6799 1.0000
1.500 0.5638 0.00993 0.00343 -0.0868 0.6687 1.0000
1.750 0.5880 0.01003 0.00347 -0.0861 0.6568 1.0000
2.000 0.6123 0.01013 0.00351 -0.0853 0.6447 1.0000
2.250 0.6366 0.01025 0.00356 -0.0845 0.6320 1.0000
2.500 0.6606 0.01038 0.00361 -0.0836 0.6169 1.0000
2.750 0.6843 0.01052 0.00367 -0.0827 0.5997 1.0000
3.000 0.7079 0.01068 0.00375 -0.0818 0.5823 1.0000
3.250 0.7318 0.01085 0.00385 -0.0809 0.5663 1.0000
3.500 0.7559 0.01103 0.00398 -0.0801 0.5512 1.0000
3.750 0.7799 0.01122 0.00412 -0.0794 0.5363 1.0000
4.000 0.8037 0.01143 0.00427 -0.0785 0.5203 1.0000
4.250 0.8272 0.01166 0.00444 -0.0777 0.5035 1.0000
4.500 0.8506 0.01190 0.00464 -0.0768 0.4863 1.0000
4.750 0.8740 0.01215 0.00485 -0.0760 0.4697 1.0000
5.000 0.8972 0.01243 0.00507 -0.0751 0.4532 1.0000
5.250 0.9201 0.01272 0.00533 -0.0742 0.4363 1.0000
5.500 0.9427 0.01303 0.00560 -0.0732 0.4188 1.0000
5.750 0.9651 0.01336 0.00588 -0.0723 0.4007 1.0000
6.000 0.9873 0.01371 0.00620 -0.0713 0.3834 1.0000
6.250 1.0093 0.01407 0.00654 -0.0703 0.3675 1.0000
6.500 1.0312 0.01444 0.00690 -0.0693 0.3524 1.0000
6.750 1.0525 0.01485 0.00728 -0.0683 0.3363 1.0000
7.000 1.0725 0.01532 0.00769 -0.0670 0.3167 1.0000
7.250 1.0912 0.01585 0.00815 -0.0656 0.2937 1.0000
7.500 1.1091 0.01642 0.00861 -0.0641 0.2687 1.0000
7.750 1.1272 0.01699 0.00910 -0.0626 0.2460 1.0000
8.000 1.1442 0.01761 0.00963 -0.0610 0.2239 1.0000
8.250 1.1612 0.01823 0.01020 -0.0595 0.2032 1.0000
8.500 1.1774 0.01888 0.01079 -0.0578 0.1835 1.0000
8.750 1.1915 0.01959 0.01143 -0.0559 0.1646 1.0000
9.000 1.2052 0.02033 0.01211 -0.0538 0.1423 1.0000
9.250 1.2143 0.02139 0.01298 -0.0514 0.1057 1.0000
9.500 1.2178 0.02289 0.01420 -0.0483 0.0694 1.0000
9.750 1.2230 0.02433 0.01551 -0.0456 0.0474 1.0000
10.000 1.2310 0.02561 0.01677 -0.0434 0.0386 1.0000
10.250 1.2384 0.02695 0.01811 -0.0412 0.0337 1.0000
10.500 1.2484 0.02811 0.01939 -0.0394 0.0308 1.0000
10.750 1.2558 0.02951 0.02086 -0.0375 0.0285 1.0000
11.000 1.2611 0.03111 0.02254 -0.0355 0.0267 1.0000
11.250 1.2688 0.03255 0.02412 -0.0340 0.0252 1.0000
11.500 1.2750 0.03417 0.02586 -0.0325 0.0237 1.0000
11.750 1.2793 0.03601 0.02779 -0.0310 0.0226 1.0000
12.000 1.2799 0.03824 0.03011 -0.0296 0.0217 1.0000
12.250 1.2810 0.04053 0.03250 -0.0284 0.0211 1.0000
12.500 1.2835 0.04276 0.03486 -0.0274 0.0204 1.0000
12.750 1.2850 0.04517 0.03739 -0.0265 0.0198 1.0000
13.000 1.2859 0.04770 0.04005 -0.0258 0.0192 1.0000
13.250 1.2861 0.05037 0.04282 -0.0253 0.0186 1.0000
13.500 1.2860 0.05317 0.04573 -0.0249 0.0180 1.0000
13.750 1.2847 0.05617 0.04883 -0.0247 0.0175 1.0000
14.000 1.2818 0.05945 0.05219 -0.0246 0.0171 1.0000
14.250 1.2766 0.06306 0.05587 -0.0247 0.0166 1.0000
14.500 1.2762 0.06623 0.05917 -0.0248 0.0163 1.0000
14.750 1.2751 0.06952 0.06259 -0.0250 0.0160 1.0000
15.000 1.2737 0.07292 0.06612 -0.0252 0.0157 1.0000
15.250 1.2721 0.07640 0.06973 -0.0256 0.0154 1.0000
15.500 1.2703 0.07997 0.07342 -0.0261 0.0151 1.0000
15.750 1.2683 0.08360 0.07717 -0.0267 0.0148 1.0000
16.000 1.2661 0.08733 0.08103 -0.0275 0.0146 1.0000
16.250 1.2636 0.09120 0.08502 -0.0284 0.0143 1.0000
16.500 1.2608 0.09520 0.08914 -0.0295 0.0140 1.0000
16.750 1.2576 0.09929 0.09333 -0.0307 0.0138 1.0000
17.000 1.2542 0.10347 0.09762 -0.0322 0.0135 1.0000
17.250 1.2507 0.10771 0.10196 -0.0337 0.0133 1.0000
17.500 1.2472 0.11197 0.10629 -0.0353 0.0131 1.0000
17.750 1.2439 0.11616 0.11056 -0.0368 0.0129 1.0000
18.000 1.2385 0.12091 0.11544 -0.0388 0.0127 1.0000
18.250 1.2314 0.12631 0.12102 -0.0414 0.0125 1.0000
18.500 1.2235 0.13195 0.12684 -0.0443 0.0124 1.0000
18.750 1.2151 0.13787 0.13294 -0.0476 0.0123 1.0000
19.000 1.2057 0.14415 0.13940 -0.0511 0.0122 1.0000
19.250 1.1951 0.15094 0.14638 -0.0552 0.0121 1.0000
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